A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.46-3.76 inch (87.8-95.5 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.98-2.28 inch (50.2-57.8 mm). The airfoil element includes at least one of a first mode with a frequency of 1056 ± 10% Hz and a second mode with a frequency of 1582 ± 10% Hz.

An engine control device may comprise a processor and a memory. The engine control device may be configured to modify a fuel flow based on a density of the fuel proximate a fuel nozzle. The engine control device may include a densimeter embedded in, or disposed proximate, the engine control device. The engine control device may include a temperature sensor embedded in, or disposed proximate, the engine control device. The engine control device may be electrically coupled to a fuel valve and/or configured to modulate the fuel valve based on a density of the fuel at the fuel valve.

An engine control device may comprise a processor and a memory. The engine control device may be configured to modify a fuel flow based on a density of the fuel proximate a fuel nozzle. The engine control device may include a densimeter embedded in, or disposed proximate, the engine control device. The engine control device may include a temperature sensor embedded in, or disposed proximate, the engine control device. The engine control device may be electrically coupled to a fuel valve and/or configured to modulate the fuel valve based on a density of the fuel at the fuel valve.

A hybrid abradable seal including a stator substrate having an external surface; a casing coupled to the external surface, the casing including radial walls extending radially from the external surface; an abradable material disposed within the casing; the abradable material and the casing being coupled together and configured to resist a deflection responsive to engine gas loads.

Apparatus and associated methods relate to simultaneously pumping and measuring density of an aircraft fuel. The aircraft fuel is pumped by a centrifugal pump having an impeller. A rotational frequency of the impeller is determined while the centrifugal pump is pumping the aircraft fuel. Flow rate of the aircraft fuel through the centrifugal pump is sensed. Pressure of the aircraft fuel is measured at two different points within or across the centrifugal pump or a differential pressure is measured between the two different points while the centrifugal pump is pumping the aircraft fuel. Density of the aircraft fuel is determined based on a head-curve relation characterizing the centrifugal pump. The head-curve relation relates the fuel density to the rotational frequency, the flow rate, and pressures at the two different points or the differential pressure between the two different points.

Apparatus and associated methods relate to simultaneously pumping and measuring density of an aircraft fuel. The aircraft fuel is pumped by a centrifugal pump having an impeller. A rotational frequency of the impeller is determined while the centrifugal pump is pumping the aircraft fuel. Flow rate of the aircraft fuel through the centrifugal pump is sensed. Pressure of the aircraft fuel is measured at two different points within or across the centrifugal pump or a differential pressure is measured between the two different points while the centrifugal pump is pumping the aircraft fuel. Density of the aircraft fuel is determined based on an empirically-determined head-curve relation corresponding to the centrifugal pump. The head-curve relation is empirically determined during a characterization phase. The empirically-determined head-curve relation relates the density of the aircraft fuel to the rotational frequency, the flow rate, and the pressures at the two different points.

A hybrid abradable seal including a stator substrate having an external surface; a casing coupled to the external surface, the casing including radial walls extending radially from the external surface; an abradable material disposed within the casing; the abradable material and the casing being coupled together and configured to resist a deflection responsive to engine gas loads.

A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component.

The present invention relates to a turbine engine comprising a wheel, (2) mounted on a shaft (4), and a disk (18), adjacent to the wheel (2) and mounted on the same shaft while being rotated by the latter. The disk (18) is made of a material having a density greater than that of the material used to manufacture the wheel (2). The invention is of use in a compressor/turbine.

A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.